Missile support system

ABSTRACT

A support system for a missile located in an underground silo to minimize shock damage to the missile wherein a cage is employed about the missile with the cage being secured directly to the missile body through a plurality of upper arms, the arms being pivotable adjacent the wall of the silo just prior to firing of the missile.

United States Patent [19] Kendall et al.

[ Dec. 9, 1975 3,148,586 9/1964 Boyle 89/18 3,170,371 2/1965 Zimmer et al. 89/l.8 3,221,602 12/1965 Price et al 89/181 3,516,628 6/1970 89/18 X 3,731,898 5/1973 Smith 89/].8 X

Primary ExaminerStephen C. Bentley Attorney, Agent, or Firm-Robert E. Geauque [57] ABSTRACT 24 Claims, 8 Drawing Figures MISSILE SUPPORT SYSTEM [75] Inventors: Giles A. Kendall, Burbank; Harish K. Bhutani, Downey; Robert Minick, Glendale, all of Calif.

[73] Assignee: Menasco Manufacturing Company,

Burbank, Calif.

[22] Filed: Dec. 21, 1973 [21] Appl. No.: 427,073

Related US. Application Data [63] Continuation of Ser. No. 224,874, Feb. 9, 1972,

abandoned.

[52] US. Cl 89/l.8; 248/18 [51] Int. Cl F411 3/04 [58] Field of Search 89/1.8, 1.8]; 248/328, 248/358 R, 18

[5 6] References Cited UNITED STATES PATENTS 3,089,389 5/1963 Andrews et al 89/181 X wi 7 y 134 94 1 i 94 9a [,ff IOO L atent Dec. 9 1975 Sheet 1 of 5 3,924,511

US, Patant Dec. 9 1975 Sheet 2 of 5 3,924,511

US. Patent D60 9 1975 Sheet 4 of 5 3,924,511

343 w Ill O Y Q D O wmm US. atant Dec. 9 1975 Sheet 5 of5 MISSILE SUPPORT SYSTEM This is a continuation, of application Ser. No. 224.874 filed Feb. 9, 1972, now abandoned.

BACKGROUND OF THE INVENTION In order to protect an intercontinental ballistic missile and keep it in a state of readiness for use at any time, the missile is stored within an underground silo. Within the silo, the missile is stored in an upright position resting on a missile support platform. The function of the missile support platform is important since the platform must support the missile in a precise location and protect the missile from ground shock. The anticipated form of ground shock which can destroy the missile would be due to a nuclear explosion adjacent the missile site.

Due to its great height, a missile in an upright position is quite vulnerable to forces which would produce a tipping action on the missile platform. Even a minor tipping at the base of the missile produces a major tipping at the top of the missile, which may be 50 feet or more above the missile base. This can result in a missile tipping over within the silo such that it rests against the silo wall. The outer skin of a missile is very thin so that the missile is quite susceptible to damage. Thus the tipping over of a missile within its concrete silo can damage it so that it is completely unsuitable for further service,

It has been found that because of the great height of the missile, only a relatively small amount of ground shock is required to effect a tipping of the missile so that the top of the missile will strike the silo wall. Actually, it is contemplated that a nuclear explosion of conventional magnitude located a substantial distance from the silo will produce sufficient ground movement to cause the missile to strike the silo wall and become inoperative. It is also contemplated that there would be no damage to the missile supporting structure, just that which occurs to the missile. It would be desirable to provide some additional support structure for the missile to protect the missile in such situations.

SUMMARY OF THE INVENTION The support system of this invention relates to the inclusion of a cage to provide additional support for the missile, the cage being connected to conventional missile support structure. Basically, the conventional missile support structure relates to a base support for the missile which is connected to the cylinder of a liquid spring. The piston of the liquid spring is connected to a series of supporting cables. The supporting cables are fixedly secured to the silo wall. As a result, the missile, supported upon the supporting base, is supported in a resilient manner with respect to the silo wall, thereby being able to absorb a certain amount of shock. Inclusion of the cage of this invention is secured to the supporting base and is adapted to surround the lower portion of the missile and be spaced from the missile wall a predetermined distance. Secured to the uppermost edge of the cage are a plurality of upper arms. The extremity of each of the upper arms is formed into a resilicnt saddle. The resilient saddle is adapted to come into contact in a snug manner with the missile wall. The locus of contact of the upper arms is located above the center of gravity of the missile. Each of the upper arms. just prior to firing of the missile, are to be explosively actuated to be pivoted away from the wall of the missile and adjacent the silo wall. Also secured to the cage at the lower edge of the cage are a plurality of pivotable lower arms. The lower arms are not to provide support for the missile wall but. only to provide lateral support for the cage and the missile during firing. An actuation means is connected between the upper arms and the lower arms so that upon pivoting of the upper arms, the lower arms are also caused to pivot adjacent the silo wall. Retained within the cage is located a plurality of guide rods. Each of the guide rods are connected to a supporting cable assembly. The supporting cable assembly includes an upper cable element and a lower cable element. The length of the upper cable element is substantially less than the length of the lower cable element, thereby creating a short pendulum effect which substantially increases the response of the system to strong horizontal shock pulses.

The primary functions of the system of this invention are:

1. To isolate the missile from large nuclear weapon induced ground shocks.

2. To provide an isolation system which requires the minimum free space or so-called rattle space between the missile and its launch tube.

3. To provide an isolation system which is essentially soft in the gravity and horizontal axis but stiff about the missile pitch axis in order to minimize pitching of the missile in its silo.

The primary function of the cage of this invention is to transfer large lateral loads induced by the short pendulum cables to the missile without inducing large pitching action and tipping in the missile.

BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 is an overall sectional view of a missile located in an underground silo which is supported by the system of this invention;

FIG. 2 is a bottom view of the supporting structure of this invention taken along line 22 of FIG. 1;

FIG. 3 is a fragmentary enlarged view of the lower portion of the missile supported by the system of this invention;

FIG. 4 is a top view of one of the upper arms taken along line 44 of FIG. 1;

FIG. 5 is a cross'sectional view through one of the upper arm units of this invention taken along 5-5 of FIG. 4;

FIG. 6 is a cross-sectional view through the liquid spring employed within this invention taken along line 6-6 of FIG. 1;

FIG. 7 is an overall view of one of the lower arm assemblies within this invention; and

FIG. 8 is a sectional view of the explosive nut assembly employed within this invention taken along line 8-8 of FIG. 5.

DETAILED DESCRIPTION OF THE SHOWN EMBODIMENT Referrring particularly to the drawings, there is shown in FIG. 1 a silo 10 having an upper door 12 and a tubular silo wall 14 which extends a substantial distance down into the ground 16. A missile 18 is supported within the silo 10 by means of the system 20 of this invention.

The missile l8 rests upon a support ring 22 which has an open center portion 24. Spaced uniformly a't l20intervals about the bottom of the support ring 22 are support brackets 26. Links 28 are pin connected at one end to the brackets 26 and are pin connected at their opposite end to cylinder 30. Each of the links 28 includes an extension 32 which is located intermediate its ends and it also is pin connected to the cylinder 30.

Slidingly supported within the cylinder upon bearings 34 is a guide 36. The guide 36 is thin-walled and has an elongated opening 38 therein. An inner cylinder 40 is secured to the cylinder 30 by means of bolts 42. The inner cylinder 40 cooperates within the guide 38 with such being located adjacent the wall of the guide 36 but not in contact therewith. A piston 44 is secured to the guide 36 by a nut 46. The piston 44 extends within the opening 38 and interiorly of the inner cylinder 40. A seal 48 cooperates between the inner cylinder 40 and the piston 44 to form a fluid-tight seal therebetween.

The piston head 50 of the piston 44 is snugly retained within a snubbing valve 52. Snubbing valve 52 is tubular in configuration and is fixedly secured at its ends to the inner cylinder 40. Within the inner cylinder 40 is located an elongated opening 54. Within this elongated opening 54 is located a fluid 56. Within the snubbing valve 52 are located orifices 58 which permit the fluid 56 to be transmitted interiorly and exteriorly of the valve 52. The fluid which has been found to be most desirable is dimethyl-polysiloxane silicone fluid which has excellent high compressibility and thermal stability over a wide range of temperatures. This thermal stability lends to more predictable, consistent viscous damping over the entire temperature spectrum. However, it is considered to be within the scope of this invention to employ other types of fluids or even other types of material which cannot be classified as a fluid.

The operation of the liquid spring 60 which includes the foregoing mentioned elements 30 to 58 is basically conventional in that the piston head 50, as it moves within the valve 52, moves fluid through the orifices 58. As this is accomplished. the movement is also damped. A flame splitter 62 is shown mounted above the liquid spring 60.

The guide 36 is connected to a lanyard 64 which is secured to the lower end of the silo 10. The function of the lanyard 64 will be explained further on in this specification.

The guide 36 is also pivotally connected to a plurality of links 66. The links 66 at one end thereof are pivotally connected to the guide 36 with the free end of the link 66 being pivotally secured to a supporting link 68. It is to be noted that there are three such supporting links 68, one for each link 66. One end of the supporting link 68 is pivotally connected to the cylinder 30. The free end of the supporting link 68 is pivotally connectcd to a cable element 70 of a cable assembly 72. It

is to be noted that there are also three such cable assemblies 72, each being located at 120about the ring 22.

The free end of the cable element 70 is pivotally attached to a guide rod 74. The free end of each of the guide rods 74 is pivotally secured to an upper cable element 76 of the cable assembly 72. The free end of each of the upper cable elements 76 is fixedly secured to a bracket 78. The bracket 78 is secured to the silo wall 14.

The foregoing cable assembly 72, the liquid spring 60, and the missile support base 22 is deemed to be basically conventional structure and is substantially as shown in US. Pat. No. 3.516.628. entitled Suspension System. issued June 23. W70. by the present imentor. For a more detailed discussion of such system. reference may be had to the foregoing patent if desired.

Each of the guide rods 74 are slidingly mounted within an opening 80 formed within a cage 82. The cage 82 is to be primarily composed of a pair of spaced apart rings 84 and 86. The rings 84 are connected together through three elongated braces 88 which extend above the upper ring 84 and below the lower ring 86. The lower end of-each of the braces 88 is fixedly secured to the ring 22. lt is to be noted that the cage 82 is located adjacent the missile 18 but is spaced therefrom by a predetermined distance. Actually, this distance is determined by the anticipated maximum lateral movement of the missile 18 during take-off. This maximum movement is depicted by line 90. The line 90 passes just interiorly of the interior surface of the ring 84. In other words. the innermost diameter of the cage 82 is not capable of interfering with the flight path of the missile 18 as it leaves the silo 10.

Fixedly mounted to the upper end of each of the braces 88 is a bracket 92. it is to be understood that there are three such brackets 92 located l20apart with respect to the missile 18. A supporting link 94 is pivotally mounted upon the bracket 92.

The following will describe in detail the upper arms 96 which are secured to the braces 88. Intermediate the ends of the supporting link 94 is pivotally secured a first intermediate link 98. A second intermediate link 100 is pivotally secured to the free end of the first intermediate link 98 and also is pivotally secured to the bracket 92. An extension 102 of the second intermediate link 100 is pivotally secured to a damping assembly 104. The free end of the damping assembly 104 is secured to the brace 88. Basically, the damping assembly 104 in cludes the use of a piston 105 movably mounted within a cylinder 107. The piston 105 is connected to a piston rod 103 which is connected to extension 102. During piston movement it is desired that the volume of cylincler 107 remain constant. Therefore, a piston rod 101 is connected to the aft side of piston 105 which enters cylinder 107 as rod 103 is removed.

A compressible solid material 109 is retained within the cylinder 107 of the damping assembly 104. As the piston 105 moves through the cylinder 107, the compressible solid material 109 is caused to move through a unidirectional check valve 111 from one side of the piston 105 to the other side of the piston 105. Upon the piston rod 103 being completely extended, movement in the opposite direction is prevented due to check valve 111. Actually. the piston rod 103 is immovably held in this extended position by the material 109 located in the aft portion of cylinder 107.

Associated with the damping assembly 104 is a compression spring 106. The spring 106 acts between the cylinder housing and the piston rod 103. The function of the spring 106 will become apparent further on in the specification.

Connected to the second intermediate link 100 is an explosive nut 112. Nut 112 is to be actuatable by an electrical current transmitted from a source (not shown). The nut 112 is to normally cooperate with a bolt 114. Bolt 114 is secured to a pin 116. Pin 116 is re tained within apertures formed within the bracket 92.

Upon the nut 112 being activated. the bolt 114 is released from its connection with the second intermediate bracket 110. As a result. the spring 106 of the damping assembly 104 causes the cylinder 110 to move in respect to the piston 108. This in turn causes the second intermediate bracket 100 to pivot in respect to the bracket 92 to the position shown in FIG. 5 of the drawings. Also, the first intermediate bracket 98 is caused to be pivoted as well as the supporting link 84 to the position shown in FlG. 5 of the drawingsv This pivoting movement is accomplished slowly due to the damping which occurs within the damping assembly 104. This movement continues until the roller 118, which is secured to the upper end of the supporting link 94, comes into contact with the silo wall 14. This movement is necessary prior to the firing of the missile 18 due to the fact that a portion of the upper arm 96 extends within the confines of line 90 which would hinder the flight path of the missile 18. Upon each of the arms 96 being moved adjacent the silo Wall 14, the arms are no longer in a position to hinder the flight path of the missile 18.

Fixedly secured to the upper end of the supporting link 94 is a bifurcated bracket 120. A pivot pin assembly 122 extends between the legs of the bifurcated bracket 120. An eccentric element 124 is eccentrically mounted upon pivot pin assembly 122 with the element 124 being integrally secured to a handle 126. The element 124 includes an opening 128 therethrough which is capable of being aligned with any one of the apertures 130 which are formed within the bifurcated legs of the bracket 120. Upon alignment of the opening 128 with any one pair of aligned apertures 130, a pin 132 is to extend through the pair of aligned apertures 130 and the opening 128. A head 134 is pivotally mounted upon the eccentric element 124. With the pin 132 removed out of cooperation with opening 128, upon manually grasping the handle 126, a person may effect rotation of the eccentric element 124 with respect to the bracket 120. Because the element 124 is eccentric, rotation of element 124 causes lineal movement of the head 134 toward and away from the supporting link 94. In this manner the adjustment of the head 134 in respect to the missile 118 may be effected.

The head 134 adjacent the missile 18 is formed into a saddle 136. Within the saddle 136 is to be located a flexible walled container 138. The material of construction of the container 138 is to normally comprise a neoprene coated nylon fabric tube. Within the container 138 is to be located a low shear strength silicone elastomer material 140. With the container in position adjacent the missile l8, lateral shock load inputs are redistributed along the container 138 through the solid media elastomer 140. This in effect acts the same as a fluid in balancing out the internal pressure. If any volume changes are introduced into the container 138, the compressible solid interior occupies a smaller volume producing a larger reactive pressure in force which is instantaneously distributed around the pad. As a result, large local loads upon the missile 18 are avoided.

A connecting link 142 is secured to the same pivot joints as the second intermediate link 100 and is adapted to move in parallel therewith. The connecting link 142 also includes an extension 144 which is similar to extension 102. The extension 144 is pivotally secured to an actuating rod 146. The actuating rod 146 extends adjacent the lower end of the cage 82 and is pivotally connected to extension 148 of a first toggle link 150. The first toggle link 150 is connected to a second toggle link 152 and to damping assembly 154. In a manner similar to the description of the damping assembly 104, the cylinder of the damping assembly 152 is connected to the free end of the second toggle link 152 with the piston of the damping assembly 154 being fixedly connected to the brace 88. The pin 156 connects together the first toggle link 150 and the second toggle link 152 in a particular fixed relationship. It is to be noted that the second toggle link 152 is slightly arcuate in configuration. The links 150 and 152 are connected together so that the line of force exerted by the spring within the damping assembly 154 is caused to exert a negative force with the links 150 and 152 shown in the solid line position of FIG. 7.

The free end of the second toggle link 150 is pivotally connected through a pin 158 to a third toggle link 160. The third toggle link 160 in turn is pivotally connected to a lower arm bracket 168. The lower arm bracket 168 is pivotally mounted by means of attaching bracket 162 to the brace 88. A low frictional roller 164 is mounted upon the free end of the lower arm bracket 168.

Upon the pivotal movement of the upper arm 96, lineal movement of the actuating rod 146 occurs. This lineal movement causes a slight pivoting movement of the links 150 and 152 resulting in the pivotal connection 158 being moved to the positive side of the toggle joint. As a result, the compression spring located within the damping assembly 154 causes the second toggle link 152 to pivot approximately degrees. Also, the first toggle link is caused to pivot approximately ninety degrees. As a result, the lower arm 168 is caused to be moved from adjacent the brace 88 to adjacent the wall of the silo 10. This movement is again clamped by a damping medium such as the silicone elastomer located within the damping assembly 154. This movement is slow and gradual until the roller 164 comes into contact with the silo wall 14. It is to be noted that the lower arm 168 is never in contact with the missile 18. It is not necessary for the lower arm 168 to contact the missile 18 since such is located adjacent the base of the missile and lateral stability can be provided by the base and is not needed by the lower arm 168. The function of the lower arms 168, there being also three in number similar to the upper arms 96, is to provide lateral stability for the cage 82 during the firing of the missile 18.

Discussing the operation of the system of this invention, it will be assumed that the system is in the position shown in solid lines within FIG. 3 of the drawings. The system of this invention is to minimize the effect of ground movement either seismically or due to an unnatural force. The ground movement is immediately transmitted through cable element 76 to the guide rod 74. In effect, the cable element 76 acts as a short pendulum. Upon a large horizontal ground movement occurring, such as what would occur in a nearby nuclear explosion, the effect of the short pendulum is to drive the missile in unison with the ground motion, thus reducing horizontal rattle space consumption.

The pendulum length is determined by two factors: (1) The ascent of rattle space; (2) The amount of lateral force the missile can take without failing. If the pendulum is too long, a relatively small ground shock will cause the missile silo to strike the missile. If the pendulum is too short, a relatively small ground shock can cause missile failure since the force of the shock is transmitted directly into the missile through the pendulum. The length of the pendulum link 76 cannot be less than the rattle space or the effect of the rattle space is decreased. if the link 76 was equal to the rattle space and the missile itself could take the increased force effect which would be transmitted through such a short length, this would be highly desirable. However, missiles are fragile structures so normally the link 76 is increased in length to lessen the force effect. However, the length of link 76 must be carefully selected to not be so great as to, in a small ground shock, cause the missile to not move, permitting the silo wall to move and strike the missile. The length of the link 76 must be selected to cause the missile to move away from the silo wall. However, the force transmitted to the missile to effect this movement must not cause any damage to the missile.

As previously discussed, the main problem to cope with is to prevent the tipping of the missile to avoid the top of the missile contacting the silo wall. To decrease the possibility of this occurring, it is desired to locate structure upon the missile which creates a moment to counter the tipping moment. This structure is the location of the upper arms 96 in contact with the missile wall. It is to be noted that the upper arms 96 usually contact the missile above the center of gravity of the missile and cage. Upon horizontal ground movement occurring, a counter-moment is applied through the arm 16 tending to counteract the tipping moment of the missile 18. The force of the horizontal ground movement is to be transmitted through the cable element 76 and guide rods 80 into the cage 82. The cage 82 in turn retransmits the force to the upper arms 96 and into the lower base ring 22. The longitudinal forces as well as some of the lateral forces are to be absorbed by the liquid spring 60. The guide rods 80 are permitted to move with respect to the cage 82 so as to effect transmission of the longitudinal forces to the liquid spring 60. As a result, the entire system provides a heretofore never achieved support for a missile which will preclude the missile from incurring damage, even in times of substantial ground shock. In other words, the missile will be protected in most instances except in a direct hit situation.

At a time just before firing of the missile 18, the explosive nut 112 is actuated resulting in pivotal movement of the arms 96 to adjacent the silo wall. Simultaneously therewith, due to actuating rod 146, the lower pivotal arms 168 are caused also to be moved adjacent the silo wall. As a result, the upper pivotal arms 96 are moved out of the firing path of the missile 18. Also, the upper arms 96 and the lower arms 168 provide a lateral support through the cage to the base ring 22 to give increased lateral stability of the missile 18 during take-off from the base ring 22. It is the normal procedure for the cage 82 to move a limited distance upwardly with the missile 18 during take-off. It is for this reason that the rollers 164 and 118 are provided so that such may be low frictionally moved upward along the silo wall. The amount of movement is determined by the length of the lanyard 64.

What is claimed as new in support of letters Patent is:

1. A missile support system to protect a missile located in an underground silo against shock damage wherein said system includes:

base support means to support the base of said missile; cage means to surround a portion of said missile, said cage means fixedly connected to said base support means but substantially spaced thereabove; lateral support means connected to said cage means, said lateral support means directly contacting the wall of said missile;

said base support means being secured to the wall of the silo by an attachment means, said attachment means including at least three cables equiangularly spaced about said missile, said attachment means to support said missile centrally located and spaced from the silo wall;

said cage means including openings, guide rod means movably mounted in said openings with the direction of the guide rod movement being substantially parallel to the longitudinal axis of the missile, said guide rod means connected to said cables.

2. The system as defined in claim 1 wherein:

each of said cables including an upper cable element and a lower cable element, each of said upper cable elements being connected to a guide rod and the silo wall, each of said lower cable elements being connected to the free end of its respective guide rod, the length of each of said upper cable elements being substantially less than the length of said lower cable elements.

3. The system as defined in claim 1 wherein:

said attachment means also includes a resilient means, said resilient means being connected intermediate said base support means and said cables, said resilient means connected by a linkage assembly to said base support means and located therebeneath.

4. The system as defined in claim 3 wherein:

said resilient means comprises a liquid spring, said liquid spring being movably mounted by said linkage assembly in respect to said base support means.

5. A missile support system to protect a missile located in an underground silo against shock damage wherein said system includes:

base support means to support the base of said missile;

cage means to surround a portion of said missile, said cage means fixedly connected to said base support means but substantially spaced thereabove;

lateral support means connected to said cage means, said lateral support means directly contacting the wall of said missile;

said lateral support means includes a plurality of upper arms, each said upper arm to contact the wall of the missile directly adjacent the missile center of gravity, each of said upper arms including a saddle to snugly contact the missile wall, each of said saddles including a resilient element to evenly distribute the contactual force about the missile wall, each of said upper arms being pivotally mounted by means to said cage means for pivoting away from the missile wall adjacent the silo wall.

6. The system as defined in claim 5 wherein:

said resilient element comprises a flexible walled container filled with a low shear strength compressible solid material.

7. The system as defined in claim 6 wherein:

a damping element connected to each of said upper arms, said damping element to damp the movement of said arms toward the silo wall, said damping element including means to lock said arms in position upon silo wall contact being achieved.

8. The system as defined in claim 5 wherein:

said lateral support means includes a plurality of lower arms, said lower arms pivotally connected by means to said cage means to be pivotable adjacent the silo wall.

9. The system as defined in claim 8 wherein:

each of said lower arms connected through an actuation means to a said upper arm, upon pivotable movement of a said upper arm its respective lower arm is caused to pivot by said actuation means.

10. A missile support system comprising:

base support means; i

cage means being fixedly connected to said base support means but substantially spaced thereabove;

lateral support means connected to the end of said cage means furthest from said base support means;

an attachment means connected to said base support means, said attachment means including at least three cables equiangularly spaced about said base support means, said attachment means to support said missile centrally located and spaced from the silo wall;

said cage means including openings, guide r'od means movably mounted in said openings with the direction of the guide rod movement being substantially parallel to the longituidinal axis of the missile, said guide rod means connected to said cables.

11. The system as defined in claim wherein:

each of the cables including an upper cable element and a lower cable element, said upper cable element connected to one end of its respective guide rod with a said lower cable element being connected to the free end of its respective guide rod, the length of said upper cable element is substantially less than said lower cable element.

12. The system as defined within claim 10 wherein:

said cage means includes a pair of spaced apart rings.

13. The system as defined within claim 10 wherein:

said attachment means also includes a resilient means, said resilient means being connected intermediate to the base support means and said cables, said resilient means connected by a linkage assembly to said base support means and located therebeneath.

14. The system as defined within claim 13 wherein:

said resilient means comprises a liquid spring, said liquid spring being movably mounted by said linkage assembly with respect to said base support means.

15. A missile support system comprising:

base support means;

cage means being connected to said base support means;

lateral support means connected to the end of said cage means furthest from said base support means;

said lateral support means includes a plurality of upper arms, each of said upper arms including a saddle, each of said saddles including a resilient element to evenly distribute a contractual force between a said upper am and a fixed object, each of said upper arms being mounted by means to said cage means for pivoting movement away from said fixed object.

16. The system as defined within claim 15 wherein:

said resilient element comprises a flexible wall container filled with a low shear strength compressible solid material. I

17. The system as defined within claim 16 wherein:

a damping element connected to each of said upper arms, said damping element to damp the pivotable movement of its respective said upper arm, said damping element including means to lock said arm in position upon achieving the maximum of said pivotable movement.

18. The system as defined within claim 15 wherein:

said lateral support means includes a plurality of lower arms, each of said lower arms pivotally connected by means to said cage means and pivotable in said outward direction with respect to said cage means.

19. The system as defined in claim 18 wherein:

each of said lower arms connected through an actuation means to a said upper arm, upon pivotal movement of said upper arm its respective lower arm is caused to pivot by said actuation means.

20. The system as defined in claim 19 wherein:

said resilient element comprises a flexible walled containerfilled with a low shear strength compressible solid material.

21. A missile support system to protect a missile located in an underground silo against shock damage wherein said system includes:

base support means to support the base of said missile;

cage means to surround a portion of said missile, said cage means connected to said base support means;

lateral support means connected to said cage means, said lateral support means directly contacting the wall of said missile;

said lateral support means includes a plurality of upper arms, each of said upper arms including a saddle to snugly contact the missile wall, each of said saddles including a resilient element to evenly distribute the contactual force about the missile wall;

each of said upper arms being pivotable away from the missile wall adjacent the silo wall;

a damping element connected to each of said upper arms, said damping element to damp the movement of said arms toward the silo wall and to lock said arms in position when wall contact is achieved; and

an explosive fastener connected to each of said upper arms, upon actuation of said explosive fastener said upper arms pivot toward the silo wall.

22. A missile support system comprising:

base support means;

cage means being connected to said base support means;

lateral support means connected to the end of said cage means furthest from said base support means;

said lateral support means includes a plurality of upper arms, each of said upper arms including a saddle, each of said sadddles including a resilient element to evenly distribute a contactual force between a said upper arm and a fixed object;

said cage means being primarily annular in configuration, each of said upper arms being pivotable outwardly in respect to said annular cage means;

a damping element connected to each of said upper arms, said damping element to damp the pivotable movement of its respective said upper arm and to lock said arm in position upon achieving the maximum of said pivotable movement;

an explosive fastener being connected to each of said upper arms, upon actuation of said explosive fastener its respective upper arm pivots in said outward direction.

23. A missile support system to protect a missile located in an underground silo against shock damage wherein said system includes:

base support means to support the base of said missile;

cage means to surround a portion of said missile, said cage means fixedly connected to said base support means but substantially spaced thereabove;

lateral support means connected to said cage means,

said lateral support means directly contacting the wall of said missile;

said base support means being secured to the wall of the silo by an attachment means, said attachment means including at least three cables equiangularly spaced about said missile, said attachment means to support said missile centrally located and spaced from the silo wall;

said cage means including openings, guide rod means movably mounted in said openings with the direction of the guide rod movement being substantially parallel to the longitudinal axis of the missile, said guide rod means connected to said cables;

said lateral support means includes a plurality of 24. A missile support system comprising:

base support means;

' cage means being fixedly connected to said base support means but substantially spaced therefrom;

lateral support means connected to the end of said cage means furthest from said base support means;

an attachment means connected to said base support means, said attachment means including at least three cables equiangularly spaced about said base support means, said attachment means tosupport said missile centrally located and spaced from the silo wall;

said cage means including openings, guide rod means movably mounted in said openings with the direction of the guide rod movement being substantially parallel to the longitudinal axis of the missile, said guide rod means connected to said cables;

said lateral support means includes a plurality of upper arms, each of said upper arms including a saddle, each of said saddles including a resilient element to evenly distribute a contactual force between a said upper arm and a fixed object, each of said upper arms being pivotally mounted by means to said cage means for pivoting away from the missile wall adjacent the silo wall. 

1. A missile support system to protect a missile located in an underground silo against shock damage wherein said system includes: base support means to support the base of said missile; cage means to surround a portion of said missile, said cage means fixedly connected to said base support means but substantially spaced thereabove; lateral support means connected to said cage means, said lateral support means directly contacting the wall of said missile; said base support means being secured to the wall of the silo by an attachment means, said attachment means including at least three cables equiangularly spaced about said missile, said attachment means to support said missile centrally located and spaced from the silo wall; said cage means including openings, guide rod means movably mounted in said openings with the direction of the guide rod movement being substantially parallel to the longitudinal axis of the missile, said guide rod means connected to said cables.
 2. The system as defined in claim 1 wherein: each of said cables including an upper cable element and a lower cable element, each of said upper cable elements being connected to a guide rod and the silo wall, each of said lower cable elements being connected to the free end of its respective guide rod, the length of each of said upper cable elements being substantially less than the length of said lower cable elements.
 3. The system as defined in claim 1 wherein: said attachment means also includes a resilient means, said resilient means being connected intermediate said base support means and said cables, said resilient means connected by a linkage assembly to said base support means and located therebeneath.
 4. The system as defined in claim 3 wherein: said resilient means comprises a liquid spring, said liquid spring being movably mounted by said linkage assembly in respect to said base support means.
 5. A missile support system to protect a missile located in an underground silo against shock damage wherein said system includes: base support means to support the base of said missile; cage means to surround a portion of said missile, said cage means fixedly connected to said base support means but substantially spaced thereabove; lateral support means connected to said cage means, said lateral support means directly contacting the wall of said missile; said lateral support means includes a plurality of upper arms, each said upper arm to contact the wall of the missile directly adjacent the missile center of gravity, each of said upper arms including a saddle to snugly contact the missile wall, each of said saddles including a resilient element to evenly distribute the contactual force about the missile wall, each of said upper arms being pivotally mounted by means to said cage means for pivoting away from the missile wall adjacent the silo wall.
 6. The system as defined in claim 5 wherein: said resilient element comprises a flexible walled container filled with a low shear strength compressible solid material.
 7. The system as defined in claim 6 wherein: a damping element connected to each of said upper arms, said damping element to damp the movement of said arms toward the silo wall, said damping element including means to lock said arms in position upon silo wall contact being achieved.
 8. The system as defined in claim 5 wherein: said lateral support means includes a plurality of lower arms, said lower arms pivotally connected by means to said cage means to be pivotable adjacent the silo wall.
 9. The system as defined in claim 8 wherein: each of said lower arms connected through an actuation means to a said upper arm, upon pivotable movement of a said upper arm its respective lower arm is caused to pivot by said actuation means.
 10. A missile support system comprising: base support means; cage means being fixedly connected to said base support means but substantially spaced thereabove; lateral support means connected to the end of said cage means furthest from said base support means; an attachment means connected to said base support means, said attachment means including at least three cables equiangularly spaced about said base support means, said attachment means to support said missile centrally located and spaced from the silo wall; said cage means including openings, guide rod means movably mounted in said openings with the direction of the guide rod movement being substantially parallel to the longituidinal axis of the missile, said guide rod means connected to said cables.
 11. The system as defined in claim 10 wherein: each of the cables including an upper cable element and a lower cable element, said upper cable element connected to one end of its respective guide rod with a said lower cable element being connected to the free end of its respective guide rod, the length of said upper cable element is substantially less than said lower cable element.
 12. The system as defined within claim 10 wherein: said cage means includes a pair of spaced apart rings.
 13. The system as defined within claim 10 wherein: said attachment means also includes a resilient means, said resilient means being connected intermediate to the base support means and said cables, said resilient means connected by a linkage assembly to said base support means and located therebeneath.
 14. The system as defined within claim 13 wherein: said resilient means comprises a liquid spring, said liquid spring being movably mounted by said linkage assembly with respect to said base support means.
 15. A missile support system comprising: base support means; cage means being connected to said base support means; lateral support means connected to the end of said cage means furthest from said base support means; said lateral support means includes a plurality of upper arms, each of said upper arms including a saddle, each of said saddles including a resilient element to evenly distribute a contractual force between a said upper arm and a fixed object, each of said upper arms being mounted by means to said cage means for pivoting movement away from said fixed object.
 16. The system as defined within claim 15 wherein: said resilient element comprises a flexible wall container filled with a low shear strength compressible solid material.
 17. The system as defined within claim 16 wherein: a damping element connected to each of said upper arms, said damping element to damp the pivotable movement of its respective said upper arm, said damping element including means to lock said arm in position upon achieving the maximum of said pivotable movement.
 18. The system as defined within claim 15 wherein: said lateral support means includes a plurality of lower arms, each of said lower arms pivotally coNnected by means to said cage means and pivotable in said outward direction with respect to said cage means.
 19. The system as defined in claim 18 wherein: each of said lower arms connected through an actuation means to a said upper arm, upon pivotal movement of said upper arm its respective lower arm is caused to pivot by said actuation means.
 20. The system as defined in claim 19 wherein: said resilient element comprises a flexible walled container filled with a low shear strength compressible solid material.
 21. A missile support system to protect a missile located in an underground silo against shock damage wherein said system includes: base support means to support the base of said missile; cage means to surround a portion of said missile, said cage means connected to said base support means; lateral support means connected to said cage means, said lateral support means directly contacting the wall of said missile; said lateral support means includes a plurality of upper arms, each of said upper arms including a saddle to snugly contact the missile wall, each of said saddles including a resilient element to evenly distribute the contactual force about the missile wall; each of said upper arms being pivotable away from the missile wall adjacent the silo wall; a damping element connected to each of said upper arms, said damping element to damp the movement of said arms toward the silo wall and to lock said arms in position when wall contact is achieved; and an explosive fastener connected to each of said upper arms, upon actuation of said explosive fastener said upper arms pivot toward the silo wall.
 22. A missile support system comprising: base support means; cage means being connected to said base support means; lateral support means connected to the end of said cage means furthest from said base support means; said lateral support means includes a plurality of upper arms, each of said upper arms including a saddle, each of said sadddles including a resilient element to evenly distribute a contactual force between a said upper arm and a fixed object; said cage means being primarily annular in configuration, each of said upper arms being pivotable outwardly in respect to said annular cage means; a damping element connected to each of said upper arms, said damping element to damp the pivotable movement of its respective said upper arm and to lock said arm in position upon achieving the maximum of said pivotable movement; an explosive fastener being connected to each of said upper arms, upon actuation of said explosive fastener its respective upper arm pivots in said outward direction.
 23. A missile support system to protect a missile located in an underground silo against shock damage wherein said system includes: base support means to support the base of said missile; cage means to surround a portion of said missile, said cage means fixedly connected to said base support means but substantially spaced thereabove; lateral support means connected to said cage means, said lateral support means directly contacting the wall of said missile; said base support means being secured to the wall of the silo by an attachment means, said attachment means including at least three cables equiangularly spaced about said missile, said attachment means to support said missile centrally located and spaced from the silo wall; said cage means including openings, guide rod means movably mounted in said openings with the direction of the guide rod movement being substantially parallel to the longitudinal axis of the missile, said guide rod means connected to said cables; said lateral support means includes a plurality of upper arms, each of said upper arms including a saddle to snugly contact the missile wall, each of said saddles including a resilient element to evenly distribute the contactual force about the missile wall, each of said upper arms being piVotally mounted by means to said cage means for pivoting away from the missile wall adjacent the silo wall.
 24. A missile support system comprising: base support means; cage means being fixedly connected to said base support means but substantially spaced therefrom; lateral support means connected to the end of said cage means furthest from said base support means; an attachment means connected to said base support means, said attachment means including at least three cables equiangularly spaced about said base support means, said attachment means to support said missile centrally located and spaced from the silo wall; said cage means including openings, guide rod means movably mounted in said openings with the direction of the guide rod movement being substantially parallel to the longitudinal axis of the missile, said guide rod means connected to said cables; said lateral support means includes a plurality of upper arms, each of said upper arms including a saddle, each of said saddles including a resilient element to evenly distribute a contactual force between a said upper arm and a fixed object, each of said upper arms being pivotally mounted by means to said cage means for pivoting away from the missile wall adjacent the silo wall. 